XFOIL Version 6.94 Calculated polar for: agora10 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0630 0.04494 0.02991 0.0021 0.9988 1.0012 -2.750 -0.0458 0.04476 0.02910 -0.0005 0.9988 1.0012 -2.500 -0.0268 0.04508 0.02882 -0.0023 0.9988 1.0012 -2.250 -0.0087 0.04569 0.02887 -0.0034 0.9988 1.0012 -2.000 0.0088 0.04646 0.02915 -0.0041 0.9988 1.0012 -1.750 0.0263 0.04735 0.02961 -0.0047 0.9988 1.0012 -1.500 0.0436 0.04835 0.03023 -0.0052 0.9988 1.0012 -1.250 0.0607 0.04946 0.03101 -0.0058 0.9988 1.0012 -1.000 0.0776 0.05069 0.03197 -0.0064 0.9988 1.0012 -0.750 0.0942 0.05207 0.03313 -0.0072 0.9988 1.0012 -0.500 0.1100 0.05362 0.03452 -0.0082 0.9988 1.0012 -0.250 0.1248 0.05541 0.03619 -0.0093 0.9988 1.0012 0.000 0.1380 0.05750 0.03819 -0.0109 0.9988 1.0012 0.250 0.1493 0.05993 0.04055 -0.0127 0.9988 1.0012 0.500 0.1592 0.06267 0.04320 -0.0149 0.9988 1.0012 0.750 0.1684 0.06557 0.04600 -0.0172 0.9988 1.0012 1.000 0.1776 0.06853 0.04884 -0.0194 0.9988 1.0012 1.250 0.1871 0.07149 0.05167 -0.0216 0.9988 1.0012 1.500 0.1970 0.07444 0.05450 -0.0236 0.9988 1.0012 1.750 0.2074 0.07741 0.05734 -0.0256 0.9988 1.0012 2.000 0.2181 0.08039 0.06019 -0.0275 0.9988 1.0012 2.250 0.2290 0.08337 0.06304 -0.0294 0.9988 1.0012 2.500 0.2401 0.08635 0.06590 -0.0312 0.9988 1.0012 2.750 0.2512 0.08934 0.06877 -0.0330 0.9988 1.0012 3.000 0.2625 0.09235 0.07166 -0.0347 0.9988 1.0012 3.250 0.2739 0.09538 0.07457 -0.0364 0.9988 1.0012 3.500 0.2853 0.09842 0.07751 -0.0380 0.9988 1.0012 3.750 0.2969 0.10148 0.08046 -0.0397 0.9988 1.0012 4.000 0.3085 0.10455 0.08343 -0.0413 0.9988 1.0012 4.250 0.3201 0.10764 0.08642 -0.0429 0.9988 1.0012 4.500 0.3318 0.11074 0.08942 -0.0445 0.9988 1.0012 4.750 0.3435 0.11385 0.09245 -0.0461 0.9988 1.0012 5.000 0.3553 0.11697 0.09549 -0.0478 0.9988 1.0012